Method and apparatus for fast deploying and retrieving of towed bodies

ABSTRACT

In a method and apparatus for controlling the deployment of a towline connecting a mooring craft to an ejected object comprising the steps of monitoring velocity to determine when a point for optimum braking has been achieved and then engaging a brake system to retard deployment of the towline, a DC motor augments and controls the brake system. The DC motor further controls the retrieval of the object. A cutter mechanism uses a first blade to grip the towing cable to maintain tension thereon as a second blade cuts the cable. A spring biased boom in combination with spring biased fins on the ejected object rapidly deploys the object from its storage housing. A locking mechanism secures the deployment mechanism in a stable locked position upon the object reaching its fully extended position.

CROSS REFERENCE TO RELATED APPLICATIONS

This application is a divisional application of U.S. patent applicationSer. No. 12/630,281, filed Dec. 3, 2009, which is a divisionalapplication of U.S. patent application Ser. No. 12/009,916, filed Jan.23, 2008, now U.S. Pat. No. 7,648,101, which is a divisional applicationof U.S. patent application Ser. No. 11/029,580, filed Jan. 5, 2005, nowU.S. Pat. No. 7,429,016, which is a divisional application of U.S.patent application Ser. No. 10/671,845, filed Sep. 25, 2003, now U.S.Pat. No. 6,886,773, which is a standard patent application claiming thebenefit of Provisional Patent Application Ser. No. 60/418,520, filedOct. 15, 2002, the contents of which are incorporated herein byreference.

This application also relates to U.S. application Ser. No. 10/027,325filed Dec. 20, 2001, now U.S. Pat. No. 6,779,796; U.S. application Ser.No. 10/027,352 filed Dec. 20, 2001, now U.S. Pat. No. 6,672,543; andU.S. application Ser. No. 10/105,716 filed Mar. 25, 2002, now U.S. Pat.No. 6,683,555.

BACKGROUND OF THE INVENTION

1. Technical Field

The present invention relates to aeronautics and more particularly totrailing devices used on aircraft. Even more particularly, the inventionrelates to a system and apparatus in which a decoy stored on theaircraft is rapidly deployed for protecting the aircraft and issubsequently retrievable back into the aircraft, ready for subsequentdeployment.

2. Background Information

Aerial towed objects are used for a variety of purposes, includingdecoys, testing, and scientific investigations. In one embodiment, atowed decoy is used to draw various types of guided weapons, such asmissiles, away from an aircraft that the weapons are intended todestroy. These towed targets and decoys contain various types ofelectronic circuits to create an apparent target to a weapon whichattracts the weapon to the decoy rather than the aircraft. These typesof decoys include devices which counter infrared guided and radar guidedmissiles that pose the primary threats to military aircraft engaged in acombat environment. It will be appreciated that these missiles use theirradar guidance systems to get within striking distance of the aircraft,thereby substantially increasing their probability that the system onthe missile will be able to lock onto the target.

Current military aircraft are vulnerable to attack from surface-to-airand air-to-air missiles. Statistical data on aircraft losses in hostileactions since 1980 show that almost 90 percent of these losses have beenthe result of missile attacks. As a result, the ability to deploy decoysthat can counter guidance systems on these missiles is of great value toprotect aircraft during combat situations. To do this, the missile isdeflected away by generating a signal that causes the radar guidancesystem in the missile to think that the target is actually elsewherethan it actually is.

As the complexity and cost of bodies deployed and towed from variousaircraft increases, it becomes increasingly desirable to be able toretrieve them for reuse, while not losing the fast deployment capabilitythat currently exists with non-retrievable deployment systems. Thecurrent invention retains the existing fast deployment capability whileenabling retrieval and reuse.

The growth of fast deploy/retrievable technology requires a change inthe maintenance philosophy of the system. This change requires that anymechanism used for the deployment, tow and retraction of the body becompletely recoverable, ensuring that the body resume it's originalpre-deployed state within it's housing. The existing approach ofpyrotechnic launch and sever is no longer appropriate. The existingapproach of an ejecting aft weather shield is no longer appropriate. Theexisting approach of blind mating connectors to facilitate rapid storesreplacement is no longer worth the cost and reduced reliability.

The slow speed capability of some craft creates the need for a means ofsevering the towed body with little or no tension on the towline. Theexisting pyrotechnic approach becomes less reliable as the tension onthe cable is decreased.

There are also existing devices employing spring loaded booms to helpcontrol the separation phase of deployment. However, none are known thatuse spring loaded fins to accomplish a share of the energy storage.

In one prior art method to fast deploy, a towed body uses a solenoidbraking system. This process is not recoverable and no retrievalmechanism is available. Another prior art fast deploy launch approachuses a pyrotechnic. The existing sever approach uses a pyrotechnic. Theexisting weather protection approach uses an ejecting aft weathershield. These approaches are not recoverable and require service to theassembly before subsequent deployments. The existing connection approachuses blind mating connectors to facilitate rapid stores replacement.This approach is costly and unreliable and is no longer required.

BRIEF SUMMARY OF THE INVENTION

The system and apparatus of the present invention provides for the rapiddeployment of a decoy from a moving object, such as an aircraft, whichis connected to the aircraft by a towing cable preferably containinghigh voltage and fiber optic conductors to provide radar jamming signalsto the decoy for disrupting the flight of a weapon, such as a missile,being guided to the aircraft by radar or other guidance signals.

Another aspect of the invention is to provide the system with anejection device which rapidly deploys the decoy from its housing, whichsubsequently unwinds the cable from a spool containing a length of thetowing cable by rotating an outer, generally cylindrical or cup-shapedbailer tube about the cable supply spool, and wherein the cable passesthrough a passage in the bailer tube and then through a cutter mechanismfor severing the cable to detach the decoy from the aircraft should theneed arise.

Another feature of the invention is to mount the cable supply spool in anon-rotational manner on a double helix rotatable shaft whichreciprocates the spool along the shaft for removal of the cable from thespool, and wherein a DC motor is operatively connected to the rotatableshaft to control its rotational speed and consequently the payout speedof the cable from the spool reciprocally mounted on the shaft.

A further aspect of the invention is to provide a cutting mechanismcontaining a pair of solenoid actuated blades, one of which grips thecable to maintain tension thereon, while a second blade cuts thetensioned cable. This avoids problems occurring in prior severingsystems wherein there is insufficient tension on the cable when thesevering blade is engaged thereby eliminating the requirement fortension to be provided on the payload end of the system in order toefficiently sever the cable should the need arise after deployment ofthe decoy from the aircraft.

A further feature of the invention is to utilize a decoy with springloaded fins biased to a fully extended position, which fins are engagedwith the housing to assist in ejecting or deploying the decoy from thehousing to increase the speed of deployment, and wherein the fins areautomatically retractable into their loaded state upon the decoy beingretrieved and restored in its storage housing beneath the aircraft.

Still another aspect of the invention is to provide one or more springbiased closure doors mounted on the discharge end of the storage housingwhich automatically close after the decoy has been retrieved to assistin keeping the decoy and components free of contaminants and harshweather conditions, and in which the spring biased doors automaticallyopen upon ejection of the decoy and boom from the storage housing.

A further aspect of the invention is to provide a locking mechanismwhich secures the cable payout bailer in a locked position upon thedecoy reaching its extended position, and in which the lock remainsengaged even should electric power be lost to the locking solenoid.

In further accordance with the invention, the energy stored in thesprings which bias an extension boom to a deployment position incombination with the energy stored in the springs of the decoy fins,replace the energy heretofore obtained from pyrotechnic to rapidlydeploy the decoy. Likewise, the towed body equipped with spring loadedfins which extend upon deployment, is augmented by the use of springloaded boom to further eject the decoy and control its positionthroughout the separation phase of the deployment.

Furthermore, a DC motor is used to augment and control an optionalcentrifugal brake for the deployment of the decoy. A feedback andcontrol system controls the speed of the deploying body by allowing itto fall away from the craft and accelerates it to the craft speed bymatching separation speed to a predetermined velocity profile. Thisallows a fast deployment of the body without requiring the use of atransmission to disconnect the retrieval system and a separate brakingcontrol mechanism. A cable spool is locked by means of a fail safe pawlmechanism to tow the body without requiring a powered holding mechanism.Retrieval is accomplished by powering the DC motor to rewind the cableonto the spool. The device is fail safe such that in an unpoweredcondition the body will continue to be towed, and in the event of afailure of the spool lock actuator the body may still be retrieved.

The foregoing advantages, construction and operation of the presentinvention will become more readily apparent from the followingdescription and the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

A preferred embodiment of the invention, illustrative of the best modein which applicant contemplates applying the principles, is set forth inthe following description and is shown in the drawings and isparticularly and distinctly pointed out and set forth in the appendedclaims.

FIG. 1 is a diagrammatic view of an aircraft with a decoy being deployedtherefrom;

FIG. 2 is a perspective view of the canister, which houses the decoy anddeployment/retrieval mechanism therefor removed from the aircraft;

FIG. 3 is a diagrammatic sectional view of the decoy anddeployment/retrieval mechanism therefor mounted within the canister,which is shown in section;

FIG. 4 is an enlarged diagrammatic view of the DC motor and cable bailerassembly removed from the canister of FIG. 3;

FIG. 5 is a block diagram of three enlarged fragmentary sectional viewsof the system components shown in FIG. 3;

FIG. 5A is an enlarged fragmentary sectional view of the bailer assemblyof the deployment/retrieval mechanism;

FIG. 5B is an enlarged fragmentary sectional view showing the towingcable cutter mechanism and bailer locking mechanism of FIG. 3;

FIG. 5C is an enlarged fragmentary sectional view of a portion of thedecoy and extendable boom of FIG. 3;

FIG. 6 is a fragmentary diagrammatic perspective view of the decoymounted within the extendable boom of the deployment/retrieval mechanismwith the boom in a retracted position;

FIG. 7 is a diagrammatic perspective view showing a portion of the boommechanism shown in FIG. 6, with the decoy being removed therefrom;

FIG. 8 is a fragmentary perspective view showing the discharge end ofthe canister with the decoy starting to be deployed from the open endthereof;

FIG. 9 is an enlarged diagrammatic exploded perspective view showing thebailer locking mechanism and cutter mechanism;

FIG. 10 is an enlarged perspective view of the bailer locking mechanism;

FIG. 11 is an enlarged diagrammatic perspective view of the cuttermechanism and adjacent towing cable removed from thedeployment/retrieval mechanism; and

FIG. 12 is a schematic drawing of a feedback/control system used in apreferred embodiment of the method and apparatus of the presentinvention. Similar numerals refer to similar parts throughout thedrawings.

DETAILED DESCRIPTION OF THE INVENTION

FIG. 1 illustrates one type of aircraft indicated at 1, in which theimproved payout and retrieval system and apparatus of the presentinvention can be utilized. The system includes a housing or canister 3,which can have a rectangular shape as shown in FIG. 2, or otherconfigurations without affecting the invention. Housing 3 preferably isattached to and beneath the body of the aircraft. A decoy or other typeof towed device or body indicated generally at 5, is connected to thedeployment/retrieval apparatus by a cable 7. Decoy 5 can have variousconstructions, and preferably contains various electronic circuitriesand apparatus which sends out various jamming signals to confuse thecontrol signals supplied to an incoming missile intended to strike theaircraft. In order to provide decoy 5 with the desired radar or othermissile control jamming signals, cable 7 will contain a source ofvoltage as well as fiber optics to supply various signals thereto. Oneexample of cable 7 can be of a type described in pending patentapplication Ser. No. 60/428,156, filed Nov. 21, 2002, the contents ofwhich are incorporated herein by reference.

Housing 3 has top and bottom walls 9 and 10 and spaced side walls 11 and12 which form a hollow interior 14. As shown in FIG. 3, interior 14 isdivided into a forward decoy storage compartment 15, and an apparatuscompartment or chamber 16.

In accordance with one of the features of the invention, a bailermechanism indicated generally at 18 (FIGS. 4 and 5), is mounted withinchamber 16. Bailer mechanism 18 includes a spool 20 which contains asupply length of cable 7 and which is mounted for oscillation along ahelix shaft 22. Shaft 22 preferably is formed with a double helix, andis operatively connected to spool 20 by one or more pawls 23 which areengaged in helical grooves 24 of shaft 22. A main control shaft 26 istelescopically mounted within and extends through a hollow interior 27of helix shaft 22 and is connected by a coupler 28 to a DC drive motor30. Control shaft 26 is operatively connected to helix shaft 22 by agear train indicated generally at 31 (FIG. 5A), so that rotation ofshaft 26 by motor 30 will also rotate helix shaft 22, but at a slowerspeed than that of control shaft 26. Control shaft 26 is mounted by arear bearing 33 in a fixed bulkhead 34, which is securely mounted withinthe interior of housing 3. The forward end of control shaft 26 (FIG. 5B)terminates in a squared end 36, which secures shaft 26 to a forward hub37 so that hub 37 rotates with shaft 26. The forward end of helix shaft22 is rotatably supported by a bearing 28 on forward hub 37.

An outer bailer tub 40 is mounted about control shaft 26, helix shaft22, and spool 20, and is secured at its forward end to hub 37 byfasteners 41 (FIG. 5B) and at its rear end (FIG. 5A) by fasteners 42 toa collar 43, which is rotatably mounted by a bearing ring 44 on bulkhead34. Thus, rotation of shaft 26 will rotate bailer tube 40, as well asrotating helix shaft 22, all of which in turn are connected directly toDC motor 30 through coupler 28. A plurality of cable guide rollers 46,47, and 48 are mounted on bailer tube 40 or forward hub 37 to guide thecable from spool 20 through a solenoid locking mechanism and cuttermechanism described further below, for subsequent attachment to decoy 5.

An anti-rotation tube 35 is rigidly mounted at one end to bulkhead 34(FIG. 5A) and extends about spool 20 and is formed with a plurality oflongitudinally extending slots 39 into which pins 45 extend to preventrotation of spool 20 and assist in its oscillating movement along helixshaft 22. Pins 45 are fixedly mounted in spool hub 49 and extendoutwardly therefrom and into slots 39.

Referring to FIGS. 5A and 5B, when decoy 5 is deployed from housing 3 asdiscussed further below, tension is applied to cable 7 and will begin tounwind from spool 22, causing it to oscillate along helix shaft 22,which in turn will rotate control shaft 26 through gear train 31, whichas shown in FIG. 12, will supply signals to the control circuitry whichcontrols the speed of the deploying decoy. The control circuitry allowsdecoy 5 to fall away from the aircraft and accelerate to the aircraft'sspeed by matching separation speed to a predetermined velocity profile.This allows a fast deployment of the decoy without requiring the use ofa transmission to disconnect the retrieval system in a separate brakingcontrol mechanism as described further below. U.S. Pat. No. 5,014,997discloses one method of monitoring the velocity and total deploymentdistance of the ejected object for subsequent actuation of a brakingmechanism upon the ejected body reaching the desired deployment speedand distance. The contents of U.S. Pat, No. 5,014,997 are incorporatedherein by reference.

In accordance with another feature of the invention, the system of thepresent invention includes a unique deployment mechanism, shownparticularly in FIGS. 5C-8. Decoy 5, when stored in housing 3 rests uponan extendable boom, which is indicated generally at 50. Boom 50 ismoveably mounted in decoy storage compartment 15 (FIG. 3) and includes aplurality of guide rollers 51 (FIG. 6) which moveably suspend boom 50 ona pair of guide rails 53 which are attached to housing top wall 9. Asshown in FIG. 7, boom 50 includes a pair of spaced side walls 55 andfront and rear decoy rests 56 and 57 extending therebetween. Anintermediate decoy capstan 59 is slidably mounted between front and reardecoy rests 56 and 57 by a pair of spaced slide rods 60. A pair ofconstant force coil springs 61 are mounted on a bottom wall 62 of boom50 and a pair of deployment spring strips 63 extend along boom 50 andconnect to a pair of posts 64 which are secured to the housing sidewalls 11 and 12 so that springs 61 bias boom 50 in an outward forwarddecoy deployment direction as shown by arrow A in FIG. 7. Thus, springs61 bias boom 50 in the deployment direction of arrow A which supportsdecoy 5 in an at-rest retracted stored position within housing 3, readyfor deployment upon a deployment signal being transmitted to the bailerlocking solenoid as described further below.

In further accordance with another feature of the invention, when decoy5 is supported on extendable boom 50 and stored within housing 3, aplurality of decoy stabilizing fins 66 are in a retracted position asshown in FIGS. 6 and 8. Fins 66 are spring biased toward an outwardextended position as shown by arrows B in FIG. 8, and when in the storedposition, will engage ejection angled blocks 68, which are mounted onhousing 3 adjacent an open discharge end 69. This relationship betweenspring biased fins 66 and blocks 68 further bias decoy 5 in the ejectdirection of arrow C, as shown in FIG. 8, in addition to the biasingforce exerted thereon by springs 61.

In accordance with another feature of the invention, discharge end 69 ofhousing 3 is closed by a pair of closure doors 71 which are springbiased by springs 72 toward a closed position as shown in FIG. 3. Doors71 protect decoy 5, including the associated components and electronicconnections, etc. from exposure to the harsh surrounding atmosphere andweather which will be encountered when mounted beneath aircraft 1. Twosuch closure doors 71 are shown in FIG. 8, which when in the closedposition, form a complete closure for end opening 69. Doors 71 areopened automatically to a position as shown in FIG. 8, upon boom 50moving outwardly from housing 3 by the action of ejection springs 61 andspring biased fins 66.

In accordance with still another feature of the invention, a cuttermechanism indicated generally at 75, is mounted within housing 3,between decoy storage compartment 15 and bailer compartment 16, forsevering cable 7 should the need arise after the decoy has beendeployed. Although the present invention contemplates the retrieval ofdecoy 5 back into housing 3, certain situations can arise after it hasbeen deployed, where it becomes necessary to detach the decoy from thetowing aircraft by severing cable 7. Heretofore, pyrotechnics wasutilized to sever the cable, which has various drawbacks.

Cutter mechanism 75 includes an electric actuated rotary solenoid 77which is mounted between a front solenoid mounting plate 78 and a rearsolenoid lock plate 79. Lock plate 79 is rigidly mounted within housing3 and is connected to bulkhead 34 by a plurality of stabilizing rods 80(FIG. 5) extending therebetween. Solenoid 77 (FIG. 11) includes a pairof rotatable disks, including a front grabber disk 81 and a spaced rearcutter disk 82. Solenoid 77 is located adjacent a cable guide bracket 84which is formed with a pair of slots 85 and 86. Cable 7 moves through apassage 88 formed in bracket 84 and through slots 85 and 86. A grabberblade 90, having a saw tooth edge 91, is mounted by a fastener 92 ondisk 81 and extends outwardly therefrom, and is adapted to move intoslot 85 of bracket 84 to grip cable 7 therein. A cutter blade 94 isattached to and extends outwardly from cutter disk 82 and moves intoguide bracket slot 86 upon solenoid 77 being actuated. Should thenecessity arise for severing cable 7, solenoid 77 is actuated whichrotates disks 81 and 82 in a clockwise direction as shown in FIG. 11,bringing saw tooth edge 91 into gripping engagement with cable 7 whichwill maintain tension on cable 7 until blade 94 moves into slot 86 tosever the cable.

Heretofore, if a blade, whether actuated by pyrotechnics or other typeof force, engages cable 7, the cable may not have sufficient tensionthereon to enable the blade to completely sever the cable, dependingupon the particular position of the decoy at the time the blade is movedinto severing engagement with the cable. However, by first grippingcable 7 with blade 90, it maintains the cable under tension regardlessof the position of the decoy, enabling blade 94, which followsimmediately after blade 90 grips cable 7, to completely sever the cable.A torsional spring (not shown) is located between disks 81 and 82 tobias disk 81 and blade 90 in the clockwise direction so that blade 90maintains a gripping engagement with cable 7 as cutter blade 82 rotatesinto cutting engagement with the cable. A plurality of arcuate slots 95preferably are formed in grabber disk 81 and have stop pins 96 extendingtherethrough. This maintains grabber disk 81 in its forward-mostgripping position after solenoid 77 is energized and the torsionalspring continues to bias disk 81 in this grabbing direction.

In accordance with still another feature of the invention, a bailerlockout mechanism indicated generally at 100, is provided to lock bailermechanism 18 in a fixed non-rotatable condition after the decoy has beendeployed to its desired length. Bailer lockout mechanism 100 is bestshown in FIGS. 9 and 10, and includes a rotary solenoid 101, which ismounted in an offset relationship between plates 78 and 79. Solenoid 101includes a rotatable disk 106 which drivingly engages a rotatablymounted cam or gear 111, which in turn rotates a shaft 102 which isrotatably mounted in and extends through plate 79. Shaft 102 which isprovided with gear teeth 103 (FIG. 5B), which matingly engagecomplementary gear teeth 104 formed on the inner end of a plurality ofcams 105. Cams 105 extend radially outwardly with respect to shaft 102,and are located within an annular recess 107 formed in the rear of plate79. The outer ends of cams 105 are formed with a tooth 108 which isadapted to matingly engage gear teeth 109 formed in a control ring 110(FIG. 9) which extends into recess 107 and is fixedly connected toforward hub 37 of bailer mechanism 18 as shown in FIG. 5B. The extendedends of cams 105 are formed with holes 112 through which pins 113 extendto pivotally mount cams 105 on plate 79. Thus, as best shown in FIG. 10,upon actuation of solenoid 101, rotation of shaft 102 will pivot cams105, moving teeth 108 into engagement with gear teeth 109 of controlring 110, coupling the solenoid and in particular, cams 105, with bailermechanism 18. Thus, when teeth 108 are engaged with teeth 109 of controlring 110, it will prevent the rotation of bailer tube 40 which isattached to ring 110, and correspondingly prevent the further deploymentof cable 7 from spool 20. Thus, upon the control circuitry of FIG. 12and as discussed in U.S. Pat. No. 5,014,997, detecting that the decoyhas reached the desired extended position, lock solenoid 101 is actuatedby de-energizing the solenoid, which will rotate lock teeth 108 intoengagement with control ring 110 to prevent any further rotation ofbailer tube 40.

Solenoid shaft 102 is formed with a central hole 115 through which cable7 extends for connecting the cable to decoy 5 as shown in FIGS. 5B and5C. A plurality of posts 116 extend between spaced plates 78 and 79 toprovide the desired spacing and stability thereto. Front plate 78 isformed with a central hole 118, which aligns with hole 115 formed insolenoid shaft 102, to permit the passage of cable 7 therethrough. Whendecoy 5 is at rest within housing 3 and supported on extendable boom 50,cable 7 is under sufficient tension to maintain the decoy in housing 3,in which position outer doors 71 will be closed. In this position,bailer locking mechanism 100 is engaged, preventing the rotation ofbailer tube 40, and thus maintaining the desired tension on cable 7.

When in an at rest position, decoy 5 is retained within storagecompartment 15 by cable 7 which is wrapped about spool 20 and which isin a locked position by bailer lockout mechanism 100 as discussed above.Upon the appropriate signal being supplied to lockout mechanism 100,solenoid 101 is energized which rotates shaft 102 in a counterclockwisedirection (FIG. 10) to disengage teeth 108 from control ring teeth 109.Torsional springs 61 and spring biased fins 66 will immediately moveboom 50 and supported decoy 5 forwardly in the direction of arrow C(FIG. 8) to eject decoy 5 from housing 3. The unique combination of coilsprings 61 and spring biased fins 66 increases the ejection speed of thedecoy from the housing without the use of pyrotechnics. Cable 7 willcontinue to unwind from spool 20 by oscillating along helix shaft 22 asbailer tube 40 rotates, with cable 7 moving along and in between rollers46, 47, and 48 and through rotary solenoid shaft hole 102 of the bailerlockout mechanism, and through cable passage 88 formed in guide bracket84. Decoy 5 continues to be deployed until the desired speed and lengthof cable 7 has been reached, as discussed above, whereupon appropriatesignals are forwarded to DC motor 30. Motor 30 is energized and providesa reverse or braking effect to the motor shaft and correspondingly, tomain drive shaft 26 (FIG. 5A). Shaft 26 in turn, slows the rotation ofhelix shaft 22 through gear train 31, and correspondingly slows thereciprocal movement of spool 20 therealong. After DC motor 30 hasstopped the rotation of shafts 26 and 22 and the movement of the spool20 preventing further payout of cable 7 therefrom, bailer lockoutmechanism 100 is actuated and in particular, rotary solenoid 101, whichmoves pawl teeth 108 into locking engagement with teeth 109 of controlring 110 which is fixed to bailer tube 40, preventing any furtherrotation of the bailer assembly. As discussed above, should the needarise, cutter mechanism 75 can be actuated to sever the cable to releasedecoy 5 from being towed by aircraft 1.

However, in most situations, it is desired to retrieve decoy 5 back intohousing 3 ready for redeployment. This is accomplished easily byenergizing rotary solenoid 101 of bailer lockout mechanism 100, andenergizing DC motor 30 to rotate control shaft 26 in an oppositedirection from that of the deployment direction, which in turn willrotate helix shaft 22 and oscillate spool 20 therealong to wind cable 7about the spool, bringing decoy 5 back into position on decoy rests 56and 57 and decoy capstan 59 of extended boom 50. After decoy 5 has cometo rest on extendable boom 50, continued tension on cable 7 will movethe extended boom back into housing 3 by decoy 5 being drawn furtherinto the housing. Retraction of boom 50 will rewind spring strips 63within torsional springs 61 so that the springs are ready again toextend boom 50 should the need arise. After boom 50 is retracted,closure doors 71 are automatically pivoted to a closed position bysprings 72, sealing the end of housing 3 from contaminants. Fins 66 willfold in automatically upon entering housing 3, and will engage angledblocks 68 so that they are also in a biasing position, attempting toeject decoy 5 from housing 3. Thus, decoy 5 is in position forsubsequent deployment should the need arise without requiring anyfurther maintenance or reloading as in prior deployment systems. Asshown in FIG. 5A, the retraction force which is exerted by control shaft26 is coupled directly to the motor, which provides both the retractionforce for retrieving decoy 5, as well as the dynamic braking as thedecoy is being deployed from housing 3.

There are existing devices employing spring loaded booms to help controlthe separation phase of deployment. However, none of these devices areknown to use spring loaded fins to provide a share of the energystorage. Also, there is no known apparatus which provides for the fastdeploy, towed body assembly that uses spring loaded weather doors, zerotension cutter functionality as that of the present invention. Thepresent invention also provides a cutter assembly that uses a holdingmechanism to insert zero tension cutter functionality, and provides forsevering a towed body with zero tension on the towline.

Also, as best shown in FIG. 3, the present invention provides adeployment/retrieval system and apparatus wherein the deployment andretrieval apparatus are in alignment with the decoy instead of being ina stacked relationship as in prior systems. This provides for a morestreamlined and compact housing, as shown in FIG. 2, for mounting on anaircraft.

The method of the present invention also provides for a controlled fastdeployment, tow and retrieval of a towed body behind a craft without theuse of a transmission to disengage the retrieval mechanism or separatebrake mechanism. The device is fail safe such that in an unpoweredcondition the body will continue to be towed, and in the event of afailure of the spool lock actuator the body may still be retrieved.

The method of the present invention also provides all the requiredfunctionality in completely recoverable form. Each function operates ondeployment in one direction and reverses on retraction such that theinitial conditions for subsequent launches is the same as for theinitial launch.

While the present invention has been described in connection with thepreferred embodiments of the various figures, it is to be understoodthat other similar embodiments may be used or modifications andadditions may be made to the described embodiment for performing thesame function of the present invention without deviating therefrom.Therefore, the present invention should not be limited to any singleembodiment, but rather construed in breadth and scope in accordance withthe recitation of the appended claims.

In the foregoing description, certain terms have been used for brevity,clearness, and understanding. No unnecessary limitations are to beimplied therefrom beyond the requirement of the prior art because suchterms are used for descriptive purposes and are intended to be broadlyconstrued.

Moreover, the description and illustration of the invention is anexample and the invention is not limited to the exact details shown ordescribed.

1. In a method for controlling the deployment of a towline connecting amooring craft to an ejected object comprising the steps of monitoringthe velocity and deployment distance of the ejected object to determinewhen a point for optimum braking has been achieved; engaging a brakesystem to retard deployment of the towline when the point of optimumbraking has been achieved using a DC motor to control the brake systemby applying a reverse braking effect to a drive shaft of the DC motoroperatively connected to a spool containing the towline when the driveshaft is rotating in a deployment direction.
 2. The method defined inclaim 1 including the step of operatively connecting the spool to ahelix shaft and slowing the rotation of the drive shaft by the reversebraking effect and correspondingly of the helix shaft operativelyconnected to the drive shaft.
 3. The method defined in claim 2 ofoperatively connecting the drive shaft to the helix shaft through a geartrain.
 4. The method defined in claim 2 including the step of slowingreciprocal movement of the spool along the helix shaft upon slowing therotation of the drive shaft and helix shaft to slow the payout of thetowline from the shaft.
 5. The method defined in claim 4 including thestep of subsequently stopping the rotation of the drive shaft andoperatively connected spool by the step of applying the reverse brakingeffect to the drive shaft to prevent further payout of the towline. 6.The method defined in claim 5 including the step of locating the spoolin a bailer mechanism and mounting the bailer mechanism for oscillationalong the helix shaft.
 7. The method defined in claim 2 including thestep of providing the helix shaft with a double helix.
 8. The methoddefined in claim 2 including the step of extending the drive shaftthrough a hollow interior of the helix shaft.
 9. The method defined inclaim 6 including the step of actuating a lockout mechanism after thestep of stopping the rotation of the drive shaft and spool to preventfurther payout of the towline.
 10. The method defined in claim 9including the steps of providing the lockout mechanism with a rotarysolenoid and actuating the rotary solenoid to move a pawl into lockingengagement with the bailer mechanism preventing further rotation of thebailer mechanism.
 11. The method defined in claim 10 including the stepof energizing the rotary solenoid to move the pawl out of lockingengagement with the bailer mechanism and removing the reverse brakingeffect of the D.C. motor to rotate the drive shaft from that of thedeployment direction to wind the towline about the spool and retrievethe ejected object toward the mooring craft.